Rotating combustion chamber with continuous rearward discharge



Aug. 23, 1949. R. H. GODDARD ROTATING COMBUSTION CHAMBER WITH CONTINUOUS REARWARD DISCHARGE 2 Sheets-Sheet 1 Filed Oct. 25, 1943 1753371107. fobefijiodaafd.

by lltnuTncy 5am Aug. 23, 1949- R. H. GODDARD ROTATING COMBUSTION CHAMBER WITH CONTINUOUS REARWARD DISCHARGE 2 Sheets-Sheet 2 Filed Oct. 23, 1945 Robert HGoddafl y (ciofmey 64M. 0

Patented Aug. 23, 1949 UNITED STATES PATENT OFFICE ROTATING COMBUSTION CHAMBER WITH CONTINUOUS REARWARD DISCHARGE Robert H. Goddard, Annapolis, Md.: Esther C. Goddard, executrix oi said Robert H. Goddard, deceased, assignor of one-hall. to The Daniel and Florence Guggenheim Foundation, New York, N. Y., a corporation of New York Application October 23, 1943, Serial No. 507,416

' 13 Claims. (Cl. 6035.6)

This invention relates to a rotating combustion chamber adapted for use in rockets or rocket-type aircraft, and in which chamber combustion gases are produced which are thereafter continuously discharged from a rearwardly directed nozzle. It is advantageous to rotate such a combustion chamber at a relatively high speed to thoroughly intermingle the combustion liquids, such as gasoline and liquid oxygen. Such high speed rotation, however, subjects the combustion chamber walls to strong centrifugal outward pressure, which pressure is increased by the pressure of the gases produced by combustion.

It is the general object of my invention to counteract these strong outward pressures by mounting the combustion chamber in a stationary jacket or casing and by applying suflicient gas pressure in the space between the jacket and the chamber casing to counteract said outward pressures.

Other features of my invention relate to the provision of improved means for supplying combustion liquids to a rotating chamber and to improved means for distributing and intermingling the combustion liquids in the chamber.

My invention further relates to arrangements and combinations of parts which will be hereinafter described and more particularly pointed out in the appended claims.

Preferred forms of the invention are shown in the drawings, in which Fig. l is a sectional front elevation of my improved combustion chamber;

Fig. 1a is a partial detail section on the line la-la in Fig. 1;

Figs. 2 and 3 are partial side elevations of certain sealing discs and vanes, looking in the direction of the arrows 2 and 3 in Fig. 1;

Figs. 4 and 5 are sectional end elevations, taken respectively along the lines 4-4 and 5-5 in i 1;

Fig. 6 is a side elevation, partly in section, of centrifugally controlled means for regulating the valves which control the pressure in the jacket space;

Fig. 7 is a detail sectional side elevation, looking in the direction of the arrow l in Fig. 6;

Fig. 8 is a front elevation of a modified jacket construction;

Fig. 9 is a side elevation of a reenforced type of pressure container or jacket; and

Fig. 10 is a sectional front elevation of a further modification.

Referring particularly to Fig. 1, I have shown a combustion chamber Cv comprising an inner casing or wall lilhaving a cylindrical entrance portion II and a slightly conical discharge nozzle l2. The casing ill is shown as comprising a pair of reversely disposed hollow cones having their base edges joined along a line l3.

The chamber-C is provided with an outer wall 20, also formed of reversed hollow cones having their base edges joined at an annular partition 2| and spaced from the conical walls I 0 of the chamber C by a'seriesofribs 22 and 23.

The ribs 22 'are so disposed that, if extended, they would meet at the axis of the hollow cones. The ends of the ribs 22 adjacent the entrance portion II are curved forwardly in the direction of rotation, as indicated at 22a in Fig. l, to facilitate entrance of a combustion liquid, such as gasoline.

The ends 23a of the ribs 23 extend along the discharge nozzle l2 and are curved forwardly as shown at 23a to facilitate entrance of a second combustion liquid, such as liquid oxygen. These ribs are also curved in cross-section as shown in Fig. 1a. The ribs 23a assist movement of the liquid oxygen towards the combustion chamber C by their propeller-like action, thus avoiding interference with the flow by centrifugal action at the nozzle surface.

The gasoline is introduced through a pipe 25 and shut-oil? valve 28 to an annular space 21, communicating with the radiating passages formed between the ribs 22 which'space the inner chamber wall I!) from the outer wall 20. Each of these passages communicates through one or more small holes or feed openings 30 with the interior of the combustion chamber.

The liquid oxygen is similarly introduced through a pipe 32 and shut-oil valve 33 to an annular space 34, communicating with additional radiating passages between the inner wall ll! of the chamber 0 and the outer wall 20 thereof. The oxygen is then delivered to the chamber through openings 35, corresponding to the openings 30 but substantially spaced axially therefrom..

The openings 30 and 35 are so disposed that the liquids are discharged in converging directions, as indicated by the arrows a in Fig. 1. They thus intersect and are intimately intermingled at an annular area indicated generally by the line l3. Preferably, annular partitions or shields 40 are provided adjacent the openings 30 and 35. The combustion liquids must pass around these partitions as they are delivered from the rotating passages between the ribs 22 and 23 to the openings 30 and 35. Objectionable pumping action is avoided by omitting all ribs in the spaces within the annular partitions 40.

The combustion chamber C, entrance portion H and nozzle l2 are rotatably supported in bearings 42 and 43, and initial rotation of the chamber C may be produced by a motor M acting through a clutch 44 which may be disengaged when the chamber is rotating at a desired speed. An ignition tube 45 is mounted within the entrance portion II and is used to project a flame into the combustion chamber for initial convbustion when starting up the apparatus.

As the combustion gases are discharged from the nozzle i2, an outer and cooler portion of the gases is engaged by the inturned lip 59 of a disc The disc 5! is connected by a plurality of vanes 52 (Fig. 4) to a second disc 55 which is firmly supported on a sleeve 56. The sleeve 58 is connected to the nozzle i2 by a series of vanes 51 having curved entrance portions 51a. As the rotating combustion gases engage the lip 59 and are directed outward, they react with the curved .vanes 52 to keep the chamber C and associated parts in continued rapid rotation.

For preliminary starting purposes, gas under pressure may be supplied through a pipe 69 (Fig. 1), annular connection ti and stationary nozzles 62 to react against relatively short curved vanes 63 (Figs. 1 and e) mounted on the disc 55 at the opposite side from the vanes 52. A valve 64 controls the admission of gas through the pipe 69. This turbine construction for initial starting may be used in addition to the motor M or in substitution therefor. After the chamber C is in. full operation, the valve as may be closed.

As an aid to quick pick-up, two or more starting nozzles 69 (Figs. 1 and 5) are pivoted at 9? between a disc 69 and the outer face of the disc '59. The two discs are connected by segmental portions 89 which also act as outer stops for the nozzles 66. Pins ifl'mounted in the discs 68 and 5! act as inner stops.

At their inner ends, the nozzles 66 have side inlet openings i2, directed toward the chamber C and positioned to receive portions of the exhaust gases as they are ejected at high speed through the nozzle 62. The gases which enter the side openings '12 pass outward through the curved nozzles 66 and are discharged as indicated by the arrow 2) (Fig. 5), thus producing a further reaction which tends to increase the speed of rotation of the combustion chamber and associated parts.

Springs is (Fig. 5) normally hold the starting nozzles 66 in inward position against the stop pins 10. As the speed of the chamber increases,

a the inner ends of the nozzles 66 are swung outward by centrifugal force to the inoperative positions shown in dotted lines in Fig. 5, where they are shielded between the discs 5i and 68.

An outer casing or jacket 89 (Fig. 1) surrounds the rotating combustion chamber but is spaced outwardly therefrom. vanes 8i are provided on the inner face of the jacket 89 and extend closely adjacent the outer chamber wall 29 but do not engage therewith.

The jacket space thus formed is supplied with 4 parts and these sealing devices will now be described.

The pipe 25 (Fig. 1) for gasoline is connected between stationary discs 85, joined by outer annular portions 88 to additional stationary discs 81. Movable discs 88 are mounted to rotate between each pair of stationary discs 85 and 81, and each disc 88 is provided with radiating vanes 89 (Fig. 3) which rotate in the outwardly closed annular space and with running clearance with respect to the disc 81.

With this construction, gasoline may work outward between the stationary discs 89 and the rotating discs 88 but will be prevented from passing around the discs 88 and working inward by the centrifugal action of the vanes 89. Leakage is thus prevented without the use of packing and without metal-to-metal contact of any relatively movable parts. A drip pipe 90 and valve 9| may be used to draw off surplus gasoline from the annular space 21, and similar drip pipes 92 and valves 93 may be used to drain the outer portions of the sealing casings. Leakage is avoided, on stopping, by opening the valve 99 while idling speed is maintained by the motor M, after which the valves 93 are opened and the sealing liquid is drained.

An exactly similar construction is provided for preventing leakage of liquid oxygen introduced through the pipe 92 and valve 33 to the annular chamber 34. The explanation already given ap= plied directly thereto.

In order to prevent leakage of the jacket gas, fixed casings 95 are mounted on the jacket 59, and coacting discs 96 are mounted on the rotating outer chamber wall 20. The discs 9%; are pro= vided with relatively long radiating vanes 97 (Fig. 2) on one side and with relatively short vanes 98 on the other side. A relatively large annular space 99 in each casing 95 is partially filled with a sealing liquid, preferably mercury. Some of this will be forced around the outer edge of each disc 96 by the jacket gas pressure but is prevented from thereafter escaping toward the axis by the centrifugal action of the long radiating vanes 9?.

An effective seal is thus maintained during the operation of the rotating chamber.

It is desirable that the gas pressure in the outerjacket be applied only when the combustion chamber is rotating at substantial speed, and that the pressure be relieved when the speed of the chamber substantiallyv decreases. At any lower speed, the mercury seal will become inefiective and the jacket gas will escape. I accordingly provide the special gas control devices best shown in Figs. 6 and 7. These devices comprise an outer stationary annular casing i911 (Figs. 1 and 6) within which a disc Illl is supported on the rotating nozzle sleeve 56. The disc itl is provided with radiating vanes I02 on each side, which vanes tend to force the sealing liquid, as mercury, outward from the annular casing H96 through a pipe N34 to the interior of a control casing I05 having a diaphragm I06 mounted therein. The pipe 82 previously described congas under pressure through a pipe 82. This gas is preferably a very light gas, such as hydrogen or helium, by which pressure may be applied to the exterior of the rotating combustion chamber C but with minimum frictional resistance.

Special sealing devices are provided to prevent escape of gasoline, liquid oxygen and the jacket gas at the junctures of rotating and non-rotating nects the jacket space about the combustion chamber C with the interior of the control casing I05 but at the opposite side of the diaphragm I06.

High pressure jacket gas is supplied through a pipe I08 but any flow of this gas is commonly prevented by a supply valve I99 which acts as a check valve. An exhaust pipe H0 is similarly normally closed by a check valve III. A sliding frame H4 is mounted on the diaphragm 96 or is prior to the admission of the two liquids.

movable therewith, and this frame is provided with pins H and II 6, adapted to alternately engage and open the valves I09 and II I.

When a redetermined amount of pressure is built up by the rotating disc IIII, the diaphragm I86 and frame I I4 will be moved to the right in Fig. 6, engaging and opening the supply valve Hi9 and allowing gas under pressure to flow from the pipe I08 through the connection 82 to the pressure jacket 80 which encloses the rotating combustion chamber. When the chamber slows down, the pressure against the diaphragm I06 will be reduced and the diaphragm I06 and frame I It will move to the left to allow the supply valve m to close and to engage and open the exhaust valve III, thus relieving the gas pressure in the jacket M.

It is desirable to reduce the temperature of the gases collected by the disc 5i and flowing outward along the vanes 52. For this purpose, water is supplied through a pipe I and. valve I2I (Fig. l) to a casing I22 having an annular outlet I23. Water is thus supplied to the axial passages between the rotating vanes 51 in the annular space between the nozzle I 2 and the nozzle casing 56. This water acts to lower the temperature of the rear end of the nozzle I2 and at the same time the water is turned into steam which mingles with that portion of the exhaust gases which is diverted by the lip 50 and thus directed outward against the vanes 52 In Fig. 8 I have shown an alternative form of jacket casing I36 which is of spherical contour for greater strength, and which is of suiiicient size to enclose the combustion chamber Iii and a substantial portion of the nozzle I32. The portion of the nozzle enclosed is that which is subjected to the heaviest gas pressure. In this con struction, an additional bearing I33 may be provided for the combustion chamber within the jacket I30, but otherwise the construction is substantially as previously described.

In Fig. 9 I have indicated a spherical jacket casing I III of such size as to enclose only the double conical combustion chamber I 4 I. I have also indicated that this jacket casing I may be desirably wire bound, as indicated at I42, for increased strength. Obviously, the jacket casin I30 in Fig. 8 may be similarly reenforced.

Having described the details of construction of my improved combustion chamber, the method of operation will be readily apparent. In starting up the apparatus, the chamber C is started in rotation, either by the motor M or by the starting nozzles 62, or both. When a sufficient speed of rotation has been reached, gasoline and liquid oxygen are admitted by openin the valves 26 and Combustion is then produced by injection of a flame through the ignition tube 35, started just The speed of rotation will be increased by the action of the exhaust gases against the vanes 52 and also by discharge of exhaust gases through the curved nozzles 66. Further increase in speed of rotation causes the mercury or other liquid in the control casing I00 to act through the device I 05 and diaphragm IIIS to open the gas valve I09 and admit gas under pressure to the jacket casing 80 to ofiset the outward pressures in the rotating combustion chamber.

The nozzles 66 will move out of the path of the exhaust gases and become inoperative as normal speed is attained. The supply of gas under pressure through the nozzles 62 may then be discontinned, or the motor M may be unclutched from the combustion chamber.

The apparatus will then continue in satisfactory operation for as long a period as may be desired. To stop the apparatus, the valves 26 and 33 are closed. As combustion ceases and the speed induced by the vanes 52 drops off, the gas valve I09 will be automatically closed and the exhaust valve III will be automatically opened, thus relieving the pressure within the jacket 80.

In Fig. 10 I have shown a modified construction in which the pressure on the combustion chamber is supplied by a liquid rotating within a stationary jacket. The combustion chamber 0' may be similar to that shown in Fig. 1, with an inner wall I50 and outer wall I5I, and with vanes I52 disposed between the inner and outer walls and holding them in definite spaced relation. Additional vanes I53 are mounted on the outer surface of the outer wall I5I and rotate inside of a stationary jacket casing I54. Water or any other suitable liquid is provided in the jacket casing I54 and fills the lower part of the jacket and also the annular recesses I55 when the combustion chamber C is at rest. When the chamber is rotated, the water or other liquid is also rotated by the outer vanes I53 and builds up pressure between the outer chamber wall I5I and the jacket casing I5 3, which pressure counteracts the outward centrifugal force exerted on the rotating chamber as well as the gas pressure within the chamber. A portion of the nozzle is indicated at I56.

This construction induces more friction than the. preferred construction using gas within the stationary jacket but is simpler in design and is suitable for moderate speeds of chamber rotation.

Having thus described my invention and the advantages thereof, I do not wish to be limited to the details herein disclosed, otherwise than as set forth in the claims, but what I claim is:

1. In a rocket-type combustion apparatus, a rotatable structure comprising a combustion chamber and means to supply fuel and oxidizing elements to said chamber, means to rotate said structure during operation of said chamber, a stationary jacket surrounding said rotatable structure, and separate means to maintain gaseous pressure between said jacket and said rotatable structure to ofiset the outward pressures developed in said rotatable structure.

2. In a rocket type combustion apparatus, a combustion chamber, means to rotate said chamber during operation thereof, a stationary jacket surrounding said chamber, means to maintain gaseous pressure between said jacket and said chamber to offset the outward pressures in said chamber, and speed-responsive means by which the admission of gas to the jacket space is made dependent on the speed of rotation of said chamber.

3. In a rocket type combustion apparatus, a combustion chamber, means to rotate said chamber during operation thereof, a stationary jacket surrounding said chamber, means to maintain gaseous pressure between said jacket and said chamber to offset the outward pressures in said chamber, and speed-responsive means to admit gas to the jacket space only when said chamber is rotating at or above a predetermined speed.

4. In a rocket type combustion apparatus, a. combustion chamber, means to rotate said cham ber during operation thereof, a stationary jacket surrounding said chamber, means to maintain aaraea e gaseous premure between said jacket and said chamber to oflset the outward pressures in said chamber, and speed-responsive means to admit gas to the jacket space only when said chamber is rotating at or above a predetermined speed and to connect said jacket space to exhaust below a predetermined speed of rotation.

5. In a rocket type combustion apparatus, a combustion chamber, means to rotate said chamher during operation thereof, a stationary jacket surrounding said chamber, a supply pipe and exhaust pipe connected to said jacket, valves normally closing said pipes and controlling the supply of a pressure fluid thereto, a device operative to open a selected valve, and means to move said device in accordancewith the speed of rotation of said chamber.

6. The combination in combustion apparatus as set forth in claim 5, in which the latter means comprises a fluid pressure operated device, and in which the fluid pressure is produced by centrifugal force proportionate to the speed of rotation of said chamber.

7. In a rocket type combustion apparatus, a combustion chamber, means to rotate said chamber during operation thereof, a stationary jacket surrounding said chamber, and means to maintain gaseous pressure between said jacket and said chamber to offset the outward pressures in said chamber, and said jacket being provided with vanes to prevent rotation of the jacket gas with the rotating chamber.

8. In a rocket type combustion apparatus, a combustion chamber, means to rotate said chamber during operation thereof, a stationary jacket surrounding said chamber, means to maintain gaseous pressure between said jacket and said chamber to ofiset the outward pressures in said chamber, and liquid sealing devices to prevent jacket and between said jacket and chamber.

9. In a rocket-type combustion apparatus, a rotatable structure comprising a combustion chamber and means to supply fuel and oxidizing elements to said chamber, means to rotate said structure during operation of said chamber, a stationary jacket surrounding said rotatable structure, and separate means to produce and maintain fluid pressure between said jacket and said rotatable structure to offset the outward pressures developed in said rotatable structure.

10. In a rocket type combustion apparatus, a combustion chamber, means to rotate said chamber during operation thereof, a stationary jacket surrounding said chamber, and means to provide liquid under pressure between said jacket and said chamber to ofiset the outward pressures in said chamber, said jacket having open ends and having adjacent recessed portions of sufllcient ca-= pacity to contain the pressure liquid when the chamber is at rest.

11. In a rocket type combustion apparatus, a combustion chamber, means to rotate said chamber during operation thereof, a stationary jacket surrounding said chamber, and means to produce and maintain liquid pressure between said jacket and said chamber to offset the outward pressures in said chamber, said latter means comprising vanes on said rotating chamber having running clearance with said jacket and means to supply liquid to said vanes when the chamber is rotated and7 to store said liquid when said chamber is at res 12. In a rocket type combustion apparatus. a combustion chamber, means to rotate said chamber during operation thereof, a stationary jacket surrounding said chamber, and centrifugal means operative within said jacket and efiective to produce liquid pressure between said jacket and said chamber to offset the outward pressures in said chamber, said centrifugal means being associated with said chamber and being operative only during rotation thereof.

13. In a rocket type combustion apparatus, a combustion chamber, means to rotate said chamber during operation thereof, a stationary jacket surrounding said chamber, means to maintain fluid pressure between said jacket and said chamber to offset the outward pressures in said chamber, means to supply a combustion liquid at each end of said rotating chamber, liquid sealing means for said chamber including rotated discs and stationary enclosing casings, means to drain the space between said discs, and additional means to drain said casings when said chamber is brought to rest.

ROBERT H. GODDARD.

RHERENCES CITED The following references are of record in the flle of this patent:

UNITED STATES PATENTS Number Name Date 1,102,653 Goddard July 7, 1914 2,142,601 Bleecker Jan. 3, 1939 2,335,420 Jones Nov. 30, 1943 2,410,538 Walton Nov. 5, 1946 FOREIGN PATENTS Number Country Date 537,473 Great Britain June 24, 1941 509,757 Germain; Oct. 11, 1930 

